| 摘要 |
A gas turbine engine with dual, telescoped, independently acting rotor constructions having a multistage, axial, low-pressure compressor impeller on one rotor and a single-stage, centrifugal, high-pressure impeller on the other rotor. Casing provides separated bleed air and combustion air chambers, the former receiving air from one impeller and the latter receiving high-pressure air from the other. Control means are provided to cause one rotor to operate at constant speed and the other to operate at variable speeds necessary to meet predetermined pneumatic requirements with consequent maximum efficiency in all stages of operation whereby the lowest possible fuel consumption per mission will result.
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